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Fuel System
The Commander has two internal "wet wing" fuel tanks
located forward of the main spar in each wing. Total
fuel capacity for the 115 is 70 U.S. Gallons (68
usable). Total fuel capacity for the 115TC, and
115AT is 90 U.S. Gallons (88 usable). A reduced fuel
load indicator (located in the fuel filler necks of
90 U.S. Gallon tank models) indicates a usable fuel
capacity of 64 gallons. The 90 U.S. Gallon capacity
tanks are a recommended, no cost, option on the 115.
Approved fuel grades are 100LL (blue) and 100 grade
(green). Note: At full gross weight at takeoff, all
models have an IFR range of over 650 miles with a
1:15 reserve (30 min. to reach an alternate airport
with full 45 minute IFR reserve remaining at
landing).
The Fuel Selector is located at the mid-position on the center console, and has the following selector positions:
OFF, LEFT, BOTH, RIGHT, OFF. For takeoff and landing phases of flight, the selector should always be placed in the BOTH
position. There is a safety tab (red in color) located at the rear of the fuel selector knob. It must be depressed
while simultaneously rotating the selector knob to engage the OFF position. This prevents inadvertently shutting off the
fuel when switching tanks in flight.
Electrical System
The airplane has a 28 volt, direct current electrical system that is powered by a belt-driven alternator. A 24 volt,
lead-acid battery provides power for engine start and serves as a backup power source. The battery is located in the aft
fuselage section and is accessible through the baggage compartment. Electrical power is supplied to airplane circuits
through a main bus bar, a circuit breaker switch bus bar and a radio bus bar. The alternator capacity is 80 amperes.
The Commander is equipped with an external power plug located on the rear portion of the fuselage, aft of the baggage
door on the pilot's side.
Hydraulic System
The Commander is equipped with a hydraulic power supply unit containing a reversible electric motor-driven hydraulic
pump, fluid reservoir, pressure control valves, thermal relief valve and a gear up check valve. The hydraulic power pack
is located in the left forward area of the aft fuselage section, and is used to actuate the retractable landing gear.
Emergency Gear Extension System
The landing gear incorporates an emergency 'free-fall' system, utilizing an emergency gear extension valve which bypasses
hydraulic fluid directly to the reservoir, allowing the gear to drop by gravity within 2-3 seconds, assisted by down
springs. Emergency gear extensions may be practiced repeatedly without special service. The landing gear switch is
located in easy reach of the pilot, with gear status lights in the annunciator panel located adjacent to the activator
switch.
Brakes
Both main wheels are equipped with Cleveland self-adjusting, single-disc, dual piston hydraulic brakes which are
activated by individual master cylinders attached to the rudder pedals. A brake fluid reservoir (located in the engine
compartment) supplies system fluid to the pilot's master cylinder, which supplies fluid to the copilots brakes. Both are
activated by applying toe pressure to the tops of the rudder pedals. The parking brake uses a panel mounted control knob
and cable connected to a dual parking brake valve. It activates by depressing the toe brakes and pulling the parking
brake knob simultaneously.
Flight Controls
The Commander is equipped with dual flight controls and all-metal flight control surfaces consisting of wing flaps,
ailerons, elevators with trim tabs, and rudder. All control cables are stainless steel. The Commander is equipped with
fail-safe elevator control, with the airplane able to fly and land with only power and trim.
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